As airfoil thickness is increased, the average pressure drag, affected by leading edge vortex is reduced even to be negative, and meanwhile friction has little increase.
由于前缘涡的影响，翼型厚度增加，平均压差阻力系数变小，甚至会出现负值。
An analysis of periodic flow streamlines shows that it is probably due to the effect of leading edge vortex.
通过对沉浮运动一个周期流线图的分析，认为这是翼型前缘涡的影响造成的。
The leading edge vortex breakdown can be delayed using supplements to change the flow field over upper surface of the wing.
利用附加的小辅助件，改变翼面上方的流场，使机翼前缘肌体涡推迟破裂。
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